Cell structure thermal barrier coating

Abstract

A combustor component of a gas turbine engine includes a thermal barrier coating on a substrate, the thermal barrier coating defines a multiple of cells.

1 . A component of a gas turbine engine comprising:
 a substrate; and   a thermal barrier coating on said substrate, said thermal barrier coating defines a multiple of cells.   
     
     
         2 . The component as recited in  claim 1 , wherein said substrate defines an offset within each of said multiple of cells. 
     
     
         3 . The component as recited in  claim 2 , wherein said offset within each of said multiple of cells is a post. 
     
     
         4 . The component as recited in  claim 3 , wherein said post within each of said multiple of cells is frustro-conical. 
     
     
         5 . The component as recited in  claim 3 , wherein said post is located within a center of each of said multiple of cells. 
     
     
         6 . The component as recited in  claim 3 , wherein said post defines a height that is approximately two-thirds the thickness of said thermal barrier coating. 
     
     
         7 . The component as recited in  claim 2 , wherein said offset within each of said multiple of cells is a divot. 
     
     
         8 . The component as recited in  claim 7 , wherein said divot is located within a center of each of said multiple of cells. 
     
     
         9 . The combustor component as recited in  claim 1 , wherein each of said multiple of cells are hexagonal in shape. 
     
     
         10 . The combustor component as recited in  claim 1 , wherein each of said multiple of cells are separated by a gap. 
     
     
         11 . The combustor component as recited in  claim 1 , said substrate is a nickel base superalloy. 
     
     
         12 . A combustor component of a gas turbine engine comprising:
 a substrate which defines a multiple of offsets; and   a thermal barrier coating on said substrate, said thermal barrier coating defines a multiple of cells, each of said multiple of cells correspond with at least one of said multiple of offsets.   
     
     
         13 . The combustor component as recited in  claim 12 , wherein at least one of said multiple of offsets is a post. 
     
     
         14 . The combustor component as recited in  claim 13 , wherein said post is frustro-conical. 
     
     
         15 . The combustor component as recited in  claim 13 , wherein each of said multiple of posts is located within a center of each of said multiple of cells. 
     
     
         16 . The combustor component as recited in  claim 13 , wherein said post is approximately two-thirds the thickness of said thermal barrier coating. 
     
     
         17 . The combustor component as recited in  claim 12 , wherein at least one of said multiple of offsets is a divot. 
     
     
         18 . The combustor component as recited in  claim 17 , wherein s each of said multiple of divots is located within a center of each of said multiple of cells 
     
     
         19 . The combustor component as recited in  claim 12 , wherein each of said multiple of cells are hexagonal in shape. 
     
     
         20 . The combustor component as recited in  claim 19 , wherein each of said multiple of cells are separated by a gap.